CN101793195A - Method and system for enhancing the heat transfer of turbine engine components - Google Patents

Method and system for enhancing the heat transfer of turbine engine components Download PDF

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Publication number
CN101793195A
CN101793195A CN200910266855A CN200910266855A CN101793195A CN 101793195 A CN101793195 A CN 101793195A CN 200910266855 A CN200910266855 A CN 200910266855A CN 200910266855 A CN200910266855 A CN 200910266855A CN 101793195 A CN101793195 A CN 101793195A
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coating
metal
conjunction
thermal conductivity
containing layer
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CN200910266855A
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CN101793195B (en
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B·A·纳加拉
M·A·麦马斯特斯
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General Electric Co
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General Electric Co
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
    • C23C28/3215—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer at least one MCrAlX layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/322—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer only coatings of metal elements only
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
    • C23C28/3455—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer with a refractory ceramic layer, e.g. refractory metal oxide, ZrO2, rare earth oxides or a thermal barrier system comprising at least one refractory oxide layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/06—Metallic material
    • C23C4/08—Metallic material containing only metal elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/284—Selection of ceramic materials
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
    • Y10T428/12611—Oxide-containing component
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12771—Transition metal-base component
    • Y10T428/12861—Group VIII or IB metal-base component
    • Y10T428/12944—Ni-base component

Abstract

A method and system for enhancing the heat transfer of turbine engine components is disclosed that includes applying a metallic coating having a high thermal conductivity to the cold side of a turbine component to enhance heat transfer away from the component. The metallic coating may be roughened to improve heat transfer. The metal coating may be a Ni-Al bond coating having an aluminum content greater than about 50 weight percent.

Description

Be used to strengthen the method and system that the heat of turbine engine components is transmitted
Technical field
The disclosure is devoted to a kind of method and apparatus that is used to improve the operation of turbine engine components (component).Specifically, the disclosure relates to the turbine engine components with the coating (coating) that has strengthened hot transmission.
Background technique
Turbogenerator, for example the efficient of gas turbine is along with the improve of the combustion temperature of turbo machine (in other words as operating temperature and known) and improve.Raising on this temperature causes some lifting at least aspect the power under the situation of using identical (if not still less) fuel.Thereby the combustion temperature of expectation rising turbo machine is to raise the efficiency.
Yet, along with the combustion temperature of gas turbine raises, the metal temperature (metal temperature) of the combustion component (combustion component) that waits including, but not limited to combustion liner (combustion liner) and transition piece (in other words as conduit and known) is understood raising.Combustion liner is attached in the turbo machine, and partly defines the zone that supplies flame combustion fuel with transition piece or conduit.These parts, and other parts in the gas circuit environment suffer high temperature extremes and because aging (degradation) that bring with corrosive environment of oxidation.
The turbo machine combustion component such as, but be not limited to combustion liner, conduit, burner inflector, burner centerbody, nozzle and other constructional hardware, is formed by heat-resistant material usually.This heat-resistant material often is covered with other heat-resistant material.For example, turbine components can be formed by (wrought) superalloy that forges, and it for example is but is not limited to Hastelloy (Hasteloy alloy), Nimonic, Inconel alloy and other similar alloy.These superalloys at high temperature for example do not have desired oxidative stability under greater than about 1500 temperature.Therefore; for reduce the turbine components temperature and for provide the opposing hot combustion gas oxidation and corrosion protection; often with temperature-resistant coating, on (or in other words as hot side surface and the known) surface that is applied to turbine components under the combustion gas that are exposed to heat in conjunction with coating and thermal boundary coating (TBC).For example, turbine components can comprise the overlapping coating conduct of (thermallysprayed) MCrAlY of thermal spraying in conjunction with coating (bond coat), and (APS) zirconium oxide matrix (zirconia-based) pottery of air plasma spraying is as heat insulation TBC.Usually, TBC is with the stable zirconium oxide of yttrium.
In recent years, the ceramic top coat composition that has lower thermal conductivity (thermal conductivity) has improved running temperature, and makes the performance of the hot side that only the thermal boundary coating is applied to turbine components become nervous.Present TBC system in use finishes the work in some applications well, yet is also seeking improved coating, to reach bigger temperature-thermal cycle time performance or the temperature performance that is used for longer maintenance intervals.
Needed is a kind of like this coating system, and it has strengthened the heat transmission from turbine components, allows that turbine components moves under higher system temperature.
Summary of the invention
In an exemplary embodiment, a kind of turbo machine combustion component is disclosed, it comprises the have hot side surface substrate (substrate) of (hot side surface) and cold side surface (cold side surface) and the outer surface (outside surface) with high thermal conductivity.This outer surface is this cold side surface or second surface in conjunction with coating.
In another exemplary embodiment, a kind of thermal boundary coating system that is used for substrate is disclosed, it comprise on the hot side surface that is deposited on substrate and contacted with it first in conjunction with coating, be deposited on this first in conjunction with on the coating and contacted with it ceramic layer (ceramiclayer) and outer surface with high thermal conductivity.This outer surface is the cold side surface or second surface in conjunction with coating of this substrate.
In another exemplary embodiment, the technology that a kind of heat of improving parts is transmitted is disclosed, it comprises provides the substrate with first surface and second surface, make first in conjunction with blanket deposition on first surface and contact with it, make ceramic layer be deposited on first, and the outer surface with high thermal conductivity is provided in conjunction with on the coating and contact with it.This outer surface is this second surface or second surface in conjunction with coating.
An advantage of the present disclosure comprises the reduction in conjunction with the coating temperature.
Another advantage of the present disclosure comprises the component life of raising.
Another advantage of the present disclosure is the operation under lower cooling air delivery situation, has improved engine efficiency thus.
Another advantage of the present disclosure is utilization TBC surface under higher temperature, has improved engine efficiency thus.
Another advantage of the present disclosure is the lighter use in conjunction with coating.
Contact has shown the accompanying drawing of principle of the present disclosure in an exemplary fashion, from the more detailed description of following preferred embodiment with distinct further feature of the present disclosure and advantage
Description of drawings
Fig. 1 has shown the schematic representation in conjunction with the thermal boundary coating system of coating that has according to according to an exemplary embodiment of the present disclosure.
Fig. 2 has shown the comparison at the thermal conductivity of NiAl coating and NiCrAlY coating.
In any possible place, spread all over accompanying drawing and will use identical reference number to represent identical part.
Embodiment
In one embodiment, the disclosure is applicable to such metal parts usually, and its protection that is subjected to thermal boundary coating (TBC) system is to resist hot hostile environments.The noticeable example of this parts comprises high pressure and low-pressure turbine nozzle (stator), guard shield, combustion liner, transition piece, turbine frame and the pressurized machine hardware of gas turbine engine.Though the disclosure is specially adapted to turbine engine components, knowledge of the present disclosure is applicable to any such parts usually, that is, on these parts, thermal boundary can be used for making these parts and its environment heat to keep apart.
Fig. 1 has shown the partial cross section view according to the turbine engine components 5 of the TBC of having system of the present disclosure (coating system) 10.Turbine engine components 5 comprises substrate 20, and coating system 10 is deposited on this substrate 20.Substrate 20 comprises first surface 22 and opposing second surface 24.First surface 22 is hot side surfaces, or in other words, is the surface towards the hot running temperature of parts 5.For example, first surface 22 can be towards hot turbine gas stream.Second side surface 24 is cold side surfaces, or in other words, is the surface away from the hot running temperature of parts 5.Second side surface 24 can be towards cooled gas.In cross section shown in Figure 1, first surface 22 is parallel with second surface 24, yet in alternative layout, substrate 20 can comprise the surface of any layout that adapts with engine components 5.
In one embodiment, substrate 20 is formed by any exercisable material.For example, substrate 20 can be formed by any person in the multiple metal or metal alloy, comprises those alloy or superalloys based on nickel, cobalt and/or iron.In one embodiment, substrate 20 is made by nickel-base alloy, and in another embodiment, and substrate 20 is made by nickel-based superalloy.Nickel-based superalloy can be strengthened by the precipitation (precipitation ofgamma prime or a related phase) of the main or relevant phase of γ.In one example, nickel-based superalloy has following composition (is unit with the weight percentage): from about 4% to about 20% cobalt, from about 1% to about 10% chromium, from about 5% to about 7% aluminium, from about 0% to about 2% molybdenum, from about 3% to about 8% tungsten, from about 4% to about 12% tantalum, from about 0% to about 2% titanium, from about 0% to about 8% rhenium, from about 0% to about 6% ruthenium, from about 0% to about 1% niobium, from about 0% to about 0.1% carbon, from about 0% to about 0.01% boron, from about 0% to about 0.1% yttrium, from about 0% to about 1.5% hafnium, the nickel of aequum and subsidiary impurity.For example, suitable nickel-based superalloy can obtain by trade (brand) name Rene N5, and it has the nominal composition of the nickel and the less impurity of the carbon of by weight 7.5% cobalt, 7% chromium, 1.5% molybdenum, 6.5% tantalum, 6.2% aluminium, 5% tungsten, 3% rhenium, 0.15% hafnium, 0.004% boron and 0.05% and aequum.
According to an embodiment of the present disclosure, coating system 10 comprises and being positioned on first side surface 22 and contacted with it in conjunction with coating 30, and is positioned on second side surface 24 and contacted with it metal-containing layer (metallic layer) 32.Coating system 10 also comprises covering first ceramic layer in conjunction with coating 30.
In one embodiment, can be metal in conjunction with coating 30 and metal-containing layer 32, metallic material (metallic), intermetallic compounds (intermetallic), metal alloy, composite and its combination.Can have identical or different composition in conjunction with coating 30 and metal-containing layer 32.In one embodiment, can be NiAl in conjunction with coating 30 and metal-containing layer 32.In one embodiment, are NiAl in conjunction with coating 30, for example be mainly β NiAl phase, have limited alloyage addition.The NiAl coating can have the aluminium content from about 9% weight to about 12% weight, and aequum is mainly nickel, and in another embodiment, has the aluminium content from about 18% weight to about 21% weight, and aequum is mainly nickel.Integral body (bulk) in conjunction with coating can be made up of the formed intensive NiAl layer of depositing operation that utilizes for example air plasma spraying (APS), line electric arc spraying, high-speed oxidation fuel (HVOF) spraying and low pressure plasma spraying (LPPS) technology etc.In one embodiment, be not limited to NiAl in conjunction with coating in conjunction with the composition of coating, but can be any metal-containing coating that has suitable binding ability and temperature performance.For example, can be the NiCrAlY coating in conjunction with coating 30.Can have about 100 to about 300 microns thickness in conjunction with coating 30.Thickness in conjunction with coating can change according to parts and running environment.
According to the disclosure, metal-containing layer 32 is metal-containing material of high thermal conductivity.In one embodiment, metal-containing layer 32 has about 20 and the about thermal conductivity between 60BTU/hr ft.In another embodiment, metal-containing layer 32 has about 30 and the about high thermal conductivity between 45BTU/hr ft.In another embodiment, metal-containing layer 32 has about 38 and the about thermal conductivity between 42BTU/hr ft.In one embodiment, metal-containing layer 32 can be the NiAl coating with high thermal conductivity.For example, metal-containing layer 32 can be the NiAl that has greater than the aluminium content of about 50% weight.In one embodiment, by deposition process, for example deposit metal-containing layer 32 by air plasma spraying (APS), line electric arc spraying, high-speed oxidation fuel (HVOF) spraying and low pressure plasma spraying (LPPS) technology.In one embodiment, metal-containing layer 32 can have from about 50 to about 600 microns, more preferably from about 200 to about 400 microns thickness.The thickness of metal-containing layer 32 can change according to parts and running environment.
The comparison of the thermal conductivity by NiAl as shown in Figure 2, air plasma spraying (APS) and NiCrAlY coating can be understood the benefit of the metal-containing layer 32 of using NiAl.As can be seen from Figure 2, APS NiAl coating has high thermal conductivity on the temperature range of the operation of turbine components, and it has strengthened the heat transmission from substrate 20.
In one embodiment, as first in conjunction with coating 30, and the metal-containing layer that can use high thermal conductivity is as metal-containing layer 32 in conjunction with coating for the metal-containing that can use lower thermal conductivity.For example, in one embodiment, first in conjunction with coating 30 can be NiCrAlY in conjunction with coating, and metal-containing layer 32 can be to have the NiAl of high thermal conductivity in conjunction with coating.
In one embodiment, ceramic layer 34 can be the pottery of lower thermal conductivity.For example, the lower thermal conductivity pottery can have and is about 0.1 to 1.0BTU/ft hr °F, preferably is being thermal conductivity in 0.3 to 0.6BTU/ft hr the scope.In one embodiment, the lower thermal conductivity pottery can be the mixture of zirconium oxide, yittrium oxide, ytterbium oxide and niobium oxide (nyodenium oxide).In another embodiment, the lower thermal conductivity pottery can be the zirconium oxide (YSZ) of stabilized with yttrium oxide.In one embodiment, ceramic layer 34 can be to have the YSZ of about 3% weight to the composition of the yittrium oxide of about 10% weight.In another embodiment, ceramic layer 34 can be other stupalith, yittrium oxide for example, non-stable zirconium oxide or by other oxide, for example magnesium oxide (MgO), cerium dioxide (CeO 2), scandium oxide (Sc 2O 3) or aluminium oxide (Al 2O 3) wait and stable zirconium oxide.In other embodiment, ceramic layer 34 can comprise one or more rare earth oxides, such as, but be not limited to ytterbium oxide, scandium oxide, lanthana, neodymium oxide, erbium oxide and its combination.In this other embodiment, rare earth oxide can replace a part or all yittrium oxide in the stable zirconium oxide system.Ceramic layer 34 deposits to the thickness that is enough to provide for underlying substrate desired heat protection, usually from about 75 to about about 350 microns.As prior art in conjunction with the situation of coating under, first comprises oxide surface layer (scale) 31 in conjunction with coating 30, ceramic layer 34 is attached on it with chemical mode.
Referring to Fig. 1, metal-containing layer 32 has outer surface 36 once more.Outer surface 36 can be exposed under the low temperature of the temperature that is exposed to than ceramic layer 34.In one embodiment, outer surface 36 roughenings are between about 300 and 900 microinch, to strengthen heat transmission.In another embodiment, outer surface 36 roughenings are between about 500 and 700 microinch.The roughness of outer surface 36 can form between the depositional stage of metal-containing layer 32, and can be by control including, but not limited to the deposition process parameters of particle diameter and spraying rate etc. and controlled.Roughening can be the form of indenture and/or groove.In another embodiment, after the deposition of metal-containing layer 32, can make outer surface 36 roughenings and/or roughening extraly by roughening technology for example machinery or chemistry.
In another exemplary embodiment, metal-containing layer 32 does not exist, and outer surface 36 is second side surfaces 24 of substrate 20.In this embodiment, substrate 20 can be formed by the metal-containing composition of high thermal conductivity.In one embodiment, substrate 20 can be the metal of high thermal conductivity, metallic material, intermetallic compounds, metal alloy, composite and its combination.
In one embodiment, substrate can have about 20 and the about thermal conductivity between 60BTU/hrft.In another embodiment, substrate 20 has about 30 and the about high thermal conductivity between 45BTU/hr ft.In another embodiment, substrate 20 has about 38 and the about thermal conductivity between 42BTU/hr ft.In one embodiment, substrate 20 can be the NiAl with high thermal conductivity.For example, substrate 20 can be formed by the NiAl of the aluminium content with the aluminium that surpasses about 50% weight.In addition, but outer surface 36 is carried out roughening, to improve heat transmission.In one embodiment, outer surface 36 roughenings are between about 300 and 900 microinch, to improve heat transmission.In another embodiment, but outer surface 36 roughenings between about 500 and 700 microinch.The roughness of outer surface 36 can be formed at the shaping of substrate 20.For example, the roughness of outer surface 36 can be formed during the casting of substrate 20.Roughening can be the form of indenture and/or groove.In another embodiment, can make outer surface 36 roughenings and/or extra roughening by roughening technology for example machinery or chemistry after in conjunction with the deposition of coating 32 second.
Though the present invention has been described with reference to preferred embodiment, it will be appreciated by those skilled in the art that can carry out various variations and available equivalents substitutes its element and and can not depart from the scope of the present invention.In addition, also can make many remodeling so that specific situation or material adapt to instruction of the present invention and can not break away from essential scope of the present invention.Therefore, anticipate and seek for, the present invention is not limited to be used to realize optimal mode of the present invention and disclosed certain embodiments as being contemplated that on the contrary, the present invention will comprise falling all embodiments within the scope of the appended claims.

Claims (10)

1. a turbo machine combustion component (5), it comprises:
Substrate (2), it has hot side surface (22) and cold side surface (24); With
Outer surface with high thermal conductivity;
Wherein, described outer surface is the surface of described cold side surface (24) or metal-containing layer (32).
2. parts according to claim 1 (5) is characterized in that, described high thermal conductivity about 20 and about 60 BTU/hr ft °F between.
3. parts according to claim 1 (5) is characterized in that, described outer surface have about 300 and about 900 microinch between roughness.
4. parts according to claim 1 (5) is characterized in that, described substrate (20) is the NiAl with high thermal conductivity.
5. parts according to claim 1 (5) is characterized in that, also comprise being deposited on that described hot side surface (22) is gone up and contacted with it in conjunction with coating (30), and are deposited on and describedly go up and contacted with it ceramic layer (34) in conjunction with coating (30).
6. parts according to claim 1 (5) is characterized in that, described cold side surface (24) is described outer surface.
7. parts according to claim 1 (5) is characterized in that, described parts (5) also comprise:
Being deposited on described hot side surface (22) goes up also contacted with it in conjunction with coating (30); With
Be deposited on described in conjunction with the last also contacted with it ceramic layer (34) of coating (30);
Wherein, described outer surface is to be deposited on described cold side surface (24) to go up the also surface of contacted with it metal-containing layer (32).
8. parts according to claim 7 (5) is characterized in that, described metal-containing layer (32) is the NiAl that comprises greater than the aluminium of about 50% weight.
9. parts according to claim 8 (5) is characterized in that, described metal-containing layer (32) has the thickness between about 50 μ m and about 600 μ m.
10. parts according to claim 7 (5) is characterized in that, described metal-containing layer (32) has the thickness between about 50 μ m and about 600 μ m.
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